Note : Les descriptions sont présentées dans la langue officielle dans laquelle elles ont été soumises.
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HIGH TEMPERATURE POWDER METALLURGY SUPERALLOY WITH
ENHANCED FATIGUE & CREEP RESISTANCE
CROSS REFERENCE TO RELATED APPLICATIONS
[0001] This application is a continuation-in-part Application of U.S.
Application No. 10/651,480, filed August 29, 2003, the entire contents of
which
are hereby incorporated by reference.
BACKGROUND OF THE INVENTION
[0002] The present invention generally relates to a nickel based
superalloy composition. The present invention also relates to a component
comprising a nickel based superalloy composition.
[0003] Nickel based superalloys have been extensively used in
manufacturing gas turbine engine components. Gas turbine engines having
hotter exhaust gases and which operate at higher temperatures are more
efficient. To maximize the efficiency of gas turbine engines, attempts have
been made to form gas turbine engine components, such as turbine discs,
having higher operating temperature capabilities. In particular, there is
considerable commercial interest in superalloys for turbine and compressor
disk applications which exhibit strength and creep resistance at relatively
high
temperatures (e.g.,1300-1500° F), as well as resistance to fatigue
crack
initiation at the lower temperatures (e.g., 500-1100° F) often
experienced in
compressor and turbine disk bores. Higher temperature dwell crack growth
resistance is also a significant parameter.
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[0004] The previous generation of higher temperature capability disk
alloys of the prior art are limited to about 1200-1300° F operating
temperature,
and include such commercially used alloys as P/M Astroloy, Rene' 88 DT, and
IN100. Such disk alloys, including the most recent generation of alloys, are
typically made by inert gas atomization into powder form. The powder is
subsequently screened to an appropriate size range and consolidated by hot
compaction or by hot isostatic pressing (HIP). The consolidated powder is then
extruded into a form suitable for isothermal forging into a shape that can be
machined into an engine component. Components may also be formed by not
isostatic pressing (HIP) without the extrusion and isothermal forging steps,
and
subsequently machined to final shape. These methods of manufacture are
common throughout the industry for high gamma prime volume fraction disk
alloys.
(0005] US Patent No. 6,521,175 B1 to Mourer, et al. discloses a nickel
based superalloy which contains 1.9 to 4.0 wt. % tungsten. The superalloy of
Mourer, et al. sacrifices some low-temperature dwell fatigue crack growth
performance to achieve improved creep performance.
0006 As can be seen, there is a need for a nickel based superalloy
composition which exhibits enhanced fatigue crack initiation life at
temperatures of 500 to 1200° F, as well as enhanced resistance to creep
at
temperatures of 1200 to 1500° F. Dwell crack growth resistance at these
higher temperatures (1200 to 1500° F) is also of importance.
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SUMMARY OF THE INVENTION
[0007] In one aspect of the present invention, there is provided a nickel
based superalloy composition, comprising: Ni, Co, Cr, Mo, W, AI, Ti, Ta, Nb,
C,
B, and Zr, wherein W is present in an amount greater than 4 weight %.
[0008] In another aspect of the present invention, there is provided a
nickel based superalloy composition, comprising about 16.5 to about 20.5
weight % Co, about 9.5 to about 12.5 weight % Cr, about 1.8 to about 3.2
weight % Mo, about 4.25 to about 6.0 weight % W, about 3.0 to about 4.2
weight % AI, about 3.0 to about 4.4 weight % Ti, about 1.0 to about 2.0 weight
% Ta, about 0.6 to about 1.8 weight % Nb, about 0.01 to about 0.08 weight
C, about 0.01 to about 0.06 weight % B, and about 0.03 to about 0.15 weight
Zr, balance Ni.
[0009] In still another aspect of the present invention, there is provided a
nickel based superalloy composition, comprising about 16.8 to about 19.8
weight % Co, about 10.0 to about 12 weight % Cr, about 2.2 to about 3.0
weight % Mo, about 4.25 to about 5.5 weight % W, about 3.3 to about 3.9
weight % AI, about 3.3 to about 4.1 weight % Ti, about 1.30 to about 1.80
weight % Ta, about 0.80 to about 1.60 weight % Nb, about 0.02 to about 0.05
weight % C, about 0.02 to about 0.05 weight % B, and about 0.04 to about 0.12
weight % Zr, balance Ni.
(0010] In a further aspect of the present invention, there is provided a
nickel based superalloy composition, comprising about 17.8 to about 19.8
weight % Co, about 10.0 to about 12.0 weight % Cr, about 2.3 to about 2.9
weight % Mo, about 4.25 to about 5.0 weight % W, about 3.3 to about 3.8
weight % AI, about 3.5 to about 4.0 weight % Ti, about 1.3 to about 1.8 weight
Ta, about 0.90 to about 1.6 weight % Nb, about 0.02 to about 0.05 weight
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C, about 0.020 to about 0.040 weight % B, and about 0.05 to about 0.10 weight
Zr, balance Ni.
[0011] In still a further aspect of the present invention, there is provided
a nickel based superalloy composition, comprising about 16.8 to about 17.2
weight % Co, about 10.5 to about 12 weight % Cr, about 2.4 to about 2.8
weight % Mo, about 5.1 to about 5.5 weight % W, about 3.4 to about 3.8 weight
AI, about 3.6 to about 4.0 weight % Ti, about 1.3 to about 1.7 weight % Ta,
about 0.80 to about 1.40 weight % Nb, about 0.02 to about 0.05 weight % C,
about 0.020 to about 0.040 weight % B, and about 0.05 to about 0.10 weight
Zr, balance Ni.
[0012] In yet another aspect of the present invention, there is provided a
nickel based superalloy composition, comprising about 16.8 to about 19.8
weight % Co, about 10.0 to about 12.0 weight % Cr, about 2.2 to about 3.0
weight % Mo, about 4.25 to about 5.5 weight % W, about 3.3 to about 3.9
weight % AI, about 3.3 to about 4.1 weight % Ti, about 1.3 to about 1.8 weight
Ta, about 0.80 to about 1.60 weight % Nb, about 0.02 to about 0.05 weight
C, about 0.02 to about 0.05 weight % B, and about 0.04 to about 0.12
weight % Zr, balance Ni, wherein said superalloy has a LCF life at
1100° F, R =
0, 0.7% strain greater than about 200,000 cycles, and a time for 0.2 % creep
at
1300° F and 100 ksi greater than about 400 hours.
[0013] These and other features, aspects and advantages of the present
invention will become better understood with reference to the following
drawings, description and claims.
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BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1A is a plot showing 0.2% creep and low cycle fatigue (0.65
strain) data for alloy sample B of the invention and for a conventional alloy
(Astroloy);
5 [0015] Figure 1 B is a plot showing 0.2% creep and low cycle fatigue (0.7
strain) data for alloy samples C and D of the invention and for conventional
alloy U720 LI; and
[0016] Figure 1 C is a plot showing 0.2% creep and low cycle fatigue (0.9
strain) data for alloy samples C and D of the invention and for conventional
alloy U720 LI.
DETAILED DESCRIPTION OF THE INVENTION
[0017] The following detailed description is of the best currently
contemplated modes of carrying out the invention. The description is not to be
taken in a limiting sense, but is made merely for the purpose of illustrating
the
general principles of the invention, since the scope of the invention is best
defined by the appended claims.
[0018] The present invention provides nickel based superalloy
compositions useful for forming components for gas turbine engines, such as
compressor disks, turbine disks, disk seal plates and spacers. The superalloy
compositions of the present invention differ from prior art nickel based
superalloys (see, e.g., U.S. 6,521,175 B1 to Mourer, et al.) in that alloys of
the
invention, inter alia, contain tungsten (W) at concentrations greater than 4.0
by weight, and typically have a W content equal to or greater than about 4.25
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by weight.
[0019] Compositions of the present invention exhibit fatigue crack
initiation life at intermediate temperatures (500 to 1200° F) that are
higher by
about an order of magnitude as compared with previously disclosed superalloy
compositions. Alloys of the present invention have superior low cycle fatigue
(LCF) properties as compared with previously disclosed nickel based
superalloys. For example, alloys of the present invention may have LCF life in
excess of 470,000 cycles at 1100° F and 0.7 % strain. Additionally,
compositions of the present invention have superior dwell crack growth
resistance at higher temperatures (1200 to 1500° F), as compared with
the
current compositions U720 and Astroloy. Alloys of the present invention may
exhibit 0.2% creep values greater than about 400 hours at 1300° F and
100 ksi,
and greater than about 50 hours at 1450° F, and 65 ksi.
[0020] Alloy compositions of the present invention may be suitable for
forming gas turbine engine components, such as turbine discs and exhibit
resistance to the formation of harmful constituents such as sigma phase when
exposed to high .temperatures (1300° F+) for long periods of time. This
latter
property is commonly known in the art as "stability". Compositions are
selected
within the broad range based on proprietary calculations that predict
metallurgical stability. Alloy compositions of the present invention enable
turbine disk rim operating temperatures in excess of 1400° F, while
providing a
level of fatigue crack initiation resistance at disk bore temperatures
(typically
500 to 1100° F) at least equivalent to the highest known level of
fatigue crack
initiation resistance attainable in previously disclosed alloys having much
lower
high temperature capability as compared with alloys of the invention.
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[0021 Commonly assigned US Patent No. 6,468,368 B1 to Merrick, et
al., and commonly assigned US Patent Application Publication No.
2003/0079809 A1 also to Merrick, et al. disclose a nickel based superalloy
which contains 4.5 to 7.5 weight % (tungsten + rhenium), the disclosures of
which are incorporated by reference herein in their entirety for all purposes.
[0022] Alloy compositions disclosed by Merrick et al. (US 6,468,368)
exhibit strength and creep resistance as well as stability at high
temperatures
(e.g., 1200 to 1500° F) (see data for the sample designated as Alloy 1,
Figures
1 B-C). As will be appreciated, nickel based superalloys which have similar,
or
the same, components may have markedly different and unexpected properties
according to the proportion of the various components. For example, the
proportion of alloy components such as W, Nb, Mo, Co, and Ta can have a
major impact on the strength, creep resistance, and crack initiation
resistance
of the alloy. Applicants have now identified compositions having superior
crack growth and creep resistance at higher temperatures (1200 to 1500°
F),
and a high level of fatigue crack initiation resistance at disk bore
temperatures
(typically 500 to 1100° F), as compared with previously disclosed
compositions.
[0023 Superalloy compositions of the present invention may be produced
by inert gas atomization, and consolidated by hot isostatic pressing (HIP), or
hot compaction. The material can be used in HIP form, or may be extruded for
forging stock to make isothermally forged turbine engine disks or other
components. Such production processes are well known in the art.
[0024 In one embodiment of the invention, a nickel based superalloy
composition may comprise Ni, Co, Cr, Mo, W, AI, Ti, Ta, Nb, C, B, and Zr,
wherein W is greater than 4 weight %. More particularly, the nickel based
superalloy composition may comprise from about 16.5 to about 20.5 weight
Co, about 9.5 to about 12.5 weight % Cr, about 1.8 to about 3.2 weight % Mo,
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about 4.25 to about 6.0 weight % W, about 3.0 to about 4.2 weight % AI, about
3.0 to about 4.4 weight % Ti, about 1.0 to about 2.0 weight % Ta, about 0.06
to
about 1.8 weight % Nb, about 0.01 to about 0.08 weight % C, about 0.01 to
about 0.06 weight % B, and about 0.03 to about 0.15 weight % Zr, balance Ni.
[0025] In an exemplary embodiment of the invention, the nickel based
superalloy composition comprises from about 16.8 to about 19.8 weight % Co,
about 10.0 to about 12.0 weight % Cr, about 2.2 to about 3.0 weight % Mo,
about 4.25 to about 5.5 weight % W, about 3.3 to about 3.9 weight % AI, about
3.3 to about 4.1 weight % Ti, about 1.30 to about 1.8 weight % Ta, about 0.80
to about 1.60 weight % Nb, about 0.02 to about 0.05 weight % C, about 0.02 to
about 0.05 weight % B, and about 0.05 to about 0.12 weight % Zr, balance Ni.
[0026 In a first more preferred embodiment of the invention a nickel based
superalloy composition, which may be designated Alloy 1.1, comprises from
about 17.8 to about 19.8 weight % Co, about 10.0 to about 12.0 weight % Cr,
about 2.3 to about 2.9 weight % Mo, about 4.25 to about 5.0 weight % W,
about 3.3 to about 3.8 weight % AI, about 3.5 to about 4.0 weight % Ti, about
1.3 to about 1.8 weight % Ta, about 0.90 to about 1.60 weight % Nb, about
0.02 to about 0.050 weight % C, about 0.02 to about 0.040 weight % B, and
about 0.05 to about 0.10 weight % Zr, balance Ni. The nickel based superalloy
composition designated Alloy 1.1 may exhibit a LCF life at 800° F, R = -
1, 0.65
strain, of greater than about 260,000 cycles.
EXAMPLE 1
[0027 As an example of Alloy 1.1, the nickel based superalloy composition
includes about 18.5 weight % Co, about 11 weight % Cr, about 3.55 weight
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AI, about 2.6 weight % Mo, about 4.6 weight % W, about 3.75 weight % Ti,
about 1.5 weight % Ta, about 0.90 to about 1.60 weight % Nb, about 0.03
weight % C, about 0.03 weight % B, and about 0.075 weight % Zr, balance Ni.
For this alloy (1.1),it is of importance to note that Co content may be
increased
to levels as high as about 20% in order to reduce solvus temperature without
adversely affecting stability and properties. The mean Co content of such a
reduced solvus version of Alloy 1.1 may be about 19.25. Reduced solvus
temperature may be useful for improving ease of processing for certain
applications.
[0028 In a second more preferred embodiment of the invention, which may
be designated Alloy 1.2, a nickel based superalloy composition comprises from
about 16.8 to about 17.2 weight % Co, about 10.5 to about 12 weight % Cr,
about 2.4 to about 2.8 weight % Mo, about 5.1 to about 5.5 weight % W, about
3.4 to about 3.8 weight % AI, about 3.6 to about 4.0 weight % Ti, about 1.3 to
about 1.7 weight % Ta, about 0.85 to about 1.15 weight % Nb, about 0.02 to
about 0.05 weight % C, about 0.020 to about 0.040 weight % B, and about 0.05
to about 0.10 weight % Zr, balance Ni. This embodiment is less preferred than
the first preferred embodiment. The nickel based superalloy composition
designated Alloy 1.2 may exhibit a LCF life at 1100° F, R = 0, 0.7 %
strain, of
greater than about 470,000 cycles. Alloy 1.2 may further exhibit a time for
0.2% creep, at 1300° F and 100 ksi, of greater than about 400 hours, in
fine
grain form.
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EXAMPLE 2
[0029] As an example of Alloy 1.2, the nickel based superalloy composition
includes about 17 weight % Co, about 11.25 weight % Cr, about 3.6 weight
AI, about 2.55 weight % Mo, about 5.3 weight % W, about 3.8 weight % Ti,
5 about 1.5 weight % Ta, about 1.0 weight % Nb, about 0.03 weight % C, about
0.03 weight % B, and about 0.075 weight % Zr, balance Ni.
[0030] The embodiment of the invention generally corresponding to Alloy
1.1 has the characteristics of ease of producibility, and has a reduced solvus
10 temperature, due to increased Co content, as compared with Alloy 1.2. Alloy
1.2 may have increased high temperature creep and crack growth resistance
capability, as compared with Alloy 1.1. In light of the differences in
properties
and composition of Alloy 1.1 (e.g., Sample B, Alloy 1.1 B) in comparison with
that of Alloy 1.2 (e.g., Sample C, Alloy 1.2C), one skilled in the art may
recognize how to formulate compositions exhibiting variations of such
properties. The composition and performance characteristics of a nickel based
superalloy designated Sample D (Alloy 1.3), which is intermediate between
Alloy 1.1 and Alloy 1.2 with respect to its content of C, Cr, Co, Nb, AI, and
B, is
described in Example 3, according to one embodiment of the invention.
[0031] An alloy having a composition intermediate between those of Alloys
1.1 and 1.2 (e.g., Alloy 1.3 (Example 3)) may comprise about 17.4 weight
Co, about 11.0 weight % Cr, about 2.56 weight % Mo, about 5.5 weight % W,
about 3.64 weight % AI, about 3.8 weight % Ti, about 1.47 weight % Ta, about
0.94 weight % Nb, about 0.03 weight % C, about 0.03 weight % B, and about
0.1 weight % Zr, balance Ni. A superalloy such as Alloy 1.3 may exhibit a LCF
life, at 1100° F and 0.7 % strain, of greater than about 200,000
cycles.
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[0032] In one embodiment, nickel based superalloy compositions of the
present invention may be formed by the Powder Metallurgy (P/M) route, for
example, as described in commonly assigned US Patent No. 6,468,368 B1 to
Merrick, et al., the disclosure of which is incorporated by reference herein
in its
entirety for all purposes.
[0033] In some embodiments, nickel based superalloy compositions of the
present invention may optionally further include rhenium in an amount from 0
to
about 2.0 weight %, and usually at or near 0 weight %. Generally, rhenium
may have little or no effect on superalloy properties, but may result in a
slight
enhancement of creep performance.
[0034] In some embodiments, nickel based superalloy compositions of the
present invention may optionally further include hafnium in an amount from 0
to
about 1.0 weight %, although amounts greater than 0% may have a negative
impact on LCF properties, as seen in some prior art superalloys. Additional
elements, such as magnesium (up to 0.1 weight %), may also be added to
superalloy compositions of the invention, typically with no substantial effect
on
properties.
EXAMPLE 3
[0035] An alloy of the invention designated Sample B (Alloy 1.1 B) was
prepared having the following composition expressed as weight %: about 18.2
Co, about 11.2 % Cr, about 2.65 % Mo, about 4.8 % W, about 3.57 % AI,
about 3.86 % Ti, about 1.65 % Ta, about 0.95 % Nb, about 0.027 % C, about
0.028 % B, and about 0.07 % Zr, balance Ni. A conventional alloy (Astroloy)
was also prepared, and the fatigue and creep characteristics of HIP processed
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Sample B and Astroloy were compared. For both the Astroloy and Sample B
alloy, 270 mesh powder was used. Both the Astroloy and Sample B were
supersolvus HIP processed at about 2215° F, and solution treated to
yield a
grain size of ASTM 7 to 8. The cooling rate was about 75° F per minute
from
solution treatment temperature for both Astroloy and Sample B.
[0036] The data for LCF life at 800° F, R = -1, 0.65% strain, and time
for
0.2 % creep at 1450° F, 65 ksi for conventional Astroloy and Sample B
of the
invention are shown in Figure 1A. Under these conditions the conventional
material, Astroloy, had a LCF of 166,810 cycles. In comparison, Sample B
(Alloy 1.1B) of the invention had a LCF of 266,154 cycles. Similarly, the
conventional material, Astroloy, showed a time for 0.2 % creep at 1450°
F and
65 ksi of five (5) hours. In comparison, Sample B (Alloy 1.1 B) of the
invention
exhibited a time for 0.2 % creep at 1450° F and 65 ksi of 85 hours. The
data
from Figure 1 A is tabulated below (Table 1 ).
Table 1. LCF and 0.2% Creep Values for Sample B and PM Astroloy
Time (hours) LCF Life (cycles)
for
0.2% Creep (800 F, R =
-1,
(1450 F, 65 0.65% strain)
ksi)
Alloy Material
Sample B 85 266,154
PM Astroloy' 5 166,810
conventional superalloy
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EXAMPLE 4
[0037] An alloy of the invention designated Sample A (Alloy 1.1A) was
prepared having the following composition expressed as weight %: about 17.8
Co, about 11.0 % Cr, about 2.6 % Mo, about 5.0 % W, about 3.58 % AI,
about 3.9 % Ti, about 1.47 % Ta, about 1.03 % Nb, about 0.028 % C, about
0.028 % B, and about 0.10 % Zr, balance Ni. The fatigue and creep
characteristics of HIP processed Sample A were generally similar to those of
HIP processed Sample B as described hereinabove (Example 3 and Figure
1 A).
EXAMPLE 5
[0038] An alloy of the invention designated Sample C (Alloy 1.2C) was
prepared having the following composition expressed as weight %: about 16.9
Co, about 11.1 % Cr, about 2.55 % Mo, about 5.5 % W, about 3.79 % AI,
about 3.97 % Ti, about 1.57 % Ta, about 0.91 % Nb, about 0.033 % C, about
0.035 % B, and about 0.09 % Zr, balance Ni. Sample C was made from 270
mesh powder, hot compacted, extruded, and isothermally forged. The test
material was subsolvus solution treated to yield a grain size of ASTM 11-12.
The cooling rate from solution temperature was about 130° F per
minute.
EXAMPLE 6
[0039] A further alloy of the invention, designated Sample D (Alloy 1.3),
was prepared having the following composition expressed as weight %: about
17.4 % Co, about 11.0 % Cr, about 2.56 % Mo, about 5.5 % W, about 3.64
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AI, about 3.8 % Ti, about 1.47 % Ta, about 0.94 % Nb, about 0.03 % C, about
0.03 % B, and about 0.1 % Zr, balance Ni. Sample D was made from 270 mesh
powder, hot compacted, extruded and isothermally forged. The solution
treatment was subsolvus to yield a grain size of ASTM 10-11. The cooling rate
from solution temperature was about 500° F per minute.
(0040] The data for low cycle fatigue (LCF) life at 1100° F, R = 0,
0.7%
strain, and time for 0.2 % creep at 1300° F, 100 ksi, for Samples C and
D of the
invention are shown in Figure 1 B. For comparison, conventional alloy U720 LI
was tested under the same conditions. Alloy 1 represents an alloy composition
according to commonly assigned US Patent No. 6,468,368 B1 to Merrick et al.
Samples C and D of the invention had a LCF life of 472,876 cycles and
205,610 cycles, respectively; and a time for 0.2 % creep at 1300° F and
100 ksi
of 432 hours and 450 hours, respectively.
(0041] Under these conditions, LCF values for Samples C and D,
respectively, are almost five times (5X) and more than twice (>2X) the LCF
value for conventional alloy U720 LI. Time for 0.2 % creep for Samples C and
D of the invention is about two (2) orders of magnitude greater than that for
conventional alloy 720. It can also be seen from Figure 1 B that under the
specified test conditions, LCF values and time for 0.2 % creep for Samples C
and D are at least several fold higher than those for Alloy 1.
(0042] Data for LCF life at 1100° F, R = 0, 0.9% strain for Samples C
and D
of the invention (Examples 5 and 6) are shown in Figure 1 C. Data for the
conventional alloy, U720 LI, and for Alloy 1, tested under the same
conditions,
are included for comparison. It can be seen from Figure 1 C that under the
specified test conditions, LCF values and time for 0.2 % creep for Samples C
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and D are at least several fold higher than those for alloy U720 LI and Alloy
1.
The data from Figures 1 B and 1 C are tabulated below (Table 2).
::,
.:::
.:::
.,:.:
5 ::.:
Table 2. LCF and 0.2% Creep Values for Various Superalloys
Alloy Time (hours) LCF Life (cycles)LCF Life (cycles)
Material for (1100 F, R - 0, (1100 F, R - 0,
0.2% Creep 0.7% strain) 0.9% strain)
(1300 F, 100
ksi)
Sample C 432 472,876 221,776
Sample D 450 205,610 61,860
0720 LI 5 95,911 7,263
2
AI I oy 85 66, 550 9, 850
1 3
10 2 conventional superalloy;
3 alloy of Merrick et al. (US 6,468,368).
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[0043 It should be understood, of course, that the foregoing relates to
embodiments of the invention and that modifications may be made without
departing from the spirit and scope of the invention as set forth in the
following
claims.
